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Numerical Investigation of a Complete Scramjet Demonstrator Model for Experimental Testing Under Flight Conditions

In: High Performance Computing in Science and Engineering ‘12

Author

Listed:
  • Yann Simsont

    (Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Peter Gerlinger

    (Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Manfred Aigner

    (Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt)

Abstract

In the present paper a complete scramjet demonstrator model for experimental testing at Mach 8 is investigated numerically using the scientific code TASCOM3D (Turbulent All Speed Combustion Multigrid Solver) on the HPC vector system NEC SX-9, installed at the High Performance Computing Center Stuttgart (HLRS). First the three-dimensional intake of the model is simulated. Then the results are used as inlet conditions for the simulation of the combustor, where hydrogen is injected by a lobed strut injector located in the middle of the diverging chamber. The test conditions, corresponding to a flight speed of Mach 8 at an altitude of 30 km, and the results of the simulations are discussed in detail, occurring difficulties are highlighted. In order to ensure self-ignition and prevent the flow from blockage, potential design changes are described and investigated in order to proof their functionality. Finally the performance of the reactive and non-reactive simulations on the NEC SX-9 is analyzed.

Suggested Citation

  • Yann Simsont & Peter Gerlinger & Manfred Aigner, 2013. "Numerical Investigation of a Complete Scramjet Demonstrator Model for Experimental Testing Under Flight Conditions," Springer Books, in: Wolfgang E. Nagel & Dietmar H. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering ‘12, edition 127, pages 175-186, Springer.
    • Handle: RePEc:spr:sprchp:978-3-642-33374-3_15
    DOI: 10.1007/978-3-642-33374-3_15
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